LEMUR 2 THEODOSIA, 44863 (Decayed)

Orbit data source: Space-Track

LEMUR 2 THEODOSIA, 44863 was a payload satellite owned by Spire (US) in LEO that was launched on Wed, 11 Dec 2019 UTC via a PSLV-QL launch vehicle from the Sirharikota (SRI). Payloads include a variety of satellites, spacecraft, and rockets equipped with specific instruments for various scientific and technological missions. These include communications satellites like Starlink; space stations such as the ISS; scientific satellites like the Hubble; Earth observation satellites from companies like Planet Labs, Umbra, and HawkEye 360; GPS; miniature CubeSats for education and research; and military/defense satellites.

Not visible in the next 10 days

LEMUR 2 THEODOSIA details

Identifier	44863, 2019-089M
Orbit	Decayed
Last TLE update	3 months ago
Origin	Spire (US)
Manufacturer	Spire/Glasgow
Mission	Decayed Commercial Com/MetRO
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4.6 kg wet, 4.6 kg dry
Launch date (UTC)	2019-12-11 (5 years ago)
Launch vehicle	PSLV-QL
Launch site	Sirharikota (SRI)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.7 m
Radar Cross Section	0.124 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 3 months ago

0 LEMUR 2 THEODOSIA
1 44863U 19089M   24260.89690453  .05892667  36754-5  10562-2 0  9999
2 44863  36.9501 103.8323 0004555 291.9698  68.0602 16.31444996263206

Epoch: 2024-09-16T21:31Z

Definitive object data (Epoch: 2024-09-16T21:31:32.551Z)

Latitude	-0.00001°
Longitude	144.62733°
Altitude	186.615 km
Speed	7.797 km/s
True Right ascension	06h 55m 19s
True Declination	0° 00' 00"
Sunlit	Object was in daylight at TLE epoch

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.

Orbital elements

Apogee altitude	194.729 km
Perigee altitude	188.743 km
Semi-major axis	6,569.873 km
Eccentricity	0.0004555
Inclination	36.9501°
RAAN	103.8323°
Arg. of periapsis	291.9698°
True anomaly	68.10863°
Mean anomaly	68.0602°
Eccentric anomaly	68.08441°
Mean motion	4.07575 °/min
BSTAR	0.0010562
Orbital period	88.33 mins